airborne sensing platform for cias

• Requirements• Concept Development• Feasibility• Analysis• Synthesis• Projected Timeline

The College of Imaging Science (CIAS) requested an airborne platform to carry advanced sensing instrumentation and telemetering equipment in surveillance applications with these requirements:

Carry a 3lb payload

Has a cruise speed 15 – 30 mph

Has 1 hour endurance

Can climb 1000 ft

Fuselage Materials- Carbon, Fiberglass, Wood

Engine Location- Front, Back, Top

Propulsion- Gas, Electric, Hybrid

Batteries- Nimh, NiCad, LiPoly

Landing Gear- Trike, Tail-dragger, None at all

The winners are:– High Wing– Carbon & Fiberglass

Materials– Low tail– Front Engine– LiPoly Battery– No landing gear– Electric Engine

Wing Location Feasibility Assessment

(On a scale from 1-10) Weighting High

R1: Sufficient Skills 0.1 8

R2: Sufficient Equipment 0.1 9

R3: Sufficient # of people 0.13 2

E1: Economically Feasible 0.07 9

S1: Meeting Intermediate Milestones 0.1 8

S2: Meeting PDR Requirements 0.1 7

S3: Meeting CDR Requirements 0.15 7

T1: Has similar technology been used before 0.12 9

T2: Plane stability 0.08 9

T3: Drag reducing 0.05 8

1 7.34

Fuselage Material Feasibility Assessment

(On a scale from 1-10) Weighting Carbon

R1: Sufficient Skills 0.1 6

R2: Sufficient Equipment 0.1 9

R3: Sufficient # of people 0.13 2

E1: Economically Feasible 0.07 9

S1: Meeting Intermediate Milestones 0.1 8

S2: Meeting PDR Requirements 0.1 8

S3: Meeting CDR Requirements 0.15 7

T1: Has similar technology been used before 0.09 9

T2: Durability 0.08 9

T3: Weight 0.08 7

Total: 1 7.13

Tail Design Feasibility Assessment(On a scale from 1-10)

Weighting Low

R1: Sufficient Skills 0.1 9

R2: Sufficient Equipment 0.1 9

R3: Sufficient # of people 0.13 2

E1: Economically Feasible 0.07 8

S1: Meeting Intermediate Milestones 0.1 8

S2: Meeting PDR Requirements 0.1 8

S3: Meeting CDR Requirements 0.15 8

T1: Has similar technology been used before 0.12 8

T2: Plane stability 0.08 6

T3: Drag reducing 0.05 7

Total: 1 7.21

Engine Location Feasibility Assessment(On a scale from 1-10)

Weighting Front

R1: Sufficient Skills 0.1 8

R2: Sufficient Equipment 0.1 8

R3: Sufficient # of people 0.13 2

E1: Economically Feasible 0.07 8

S1: Meeting Intermediate Milestones 0.1 7

S2: Meeting PDR Requirements 0.1 8

S3: Meeting CDR Requirements 0.15 8

T1: Has similar technology been used before 0.12 9

T2: Plane stability 0.08 8

T3: Drag reducing 0.05 8

Total: 1 7.24

Propulsion(On a scale from

1-10) Weighting Electric

Vibration 0.3 9

Weight 0.2 8

Stability 0.2 9

Cost 0.1 7

Ease of Installation 0.2 9

Total: 1 8.6

Batteries(On a scale from 1-10) Weighting LiPoly

Energy Density (charge/mass) 0.4 9

Cost 0.1 6

Ease of use/installation 0.2 8

Recharge Ratio 0.3 7

Total: 1 7.9

Landing Gear(On a scale from

1-10) Weighting None

Aerodynamics 0.2 9

Ground Handling 0.2 0

Weight 0.3 10

Ease of Construction 0.3 10

Total: 1 7.8

WeightMotor + Motor Shelf = 1 lbCIAS Payload = 3 lbMain Battery + Receiver + small battery = 2 lbWinter/Spring Project = 1 lbTail = .2 lbFuselage = 1.8 lbWing = 3 lbTotal = ~12 lb

Some Important Equations…

D

LR

olL

L

C

CWT

S

bAR

CC

SCVL

2

2

2

1

VTP

DDD

eAR

CCC

SCVD

fuselagewingCA

LdD

D

*85.0

2

1

/

2

2

alpha knot = 4.775 rho (SL) = 0.0023769 Cd = 0.006

alpha = 4.085 rho (cruise) = 0.0023081 CL max = 1.8

Cl = 1.4 V (ft/s) = 36.67 mu = 3.74E-07

e = 0.9 weight (lb) = 12 Lf (fus length) (ft) = 4

AR = 10 time to TO (s ) = 300 dia of fuselage (ft) = 0.5

T @ TO (lb)= 2.57 mu (pavement) = 0.02 PA @ climb (ft*lbs/s) = 110

CL = 1.197696   Re (fus) = 9.06E+05  

CD (wing) = 0.056734   Cf = 4.76E-03  

S = 6.456365 ft CD (fus) = 0.004634576  

b = 8.035151 ft D (fus) = 0.106970646 lbs

D (wing) = 0.568434 lb CD (AC) = 0.072198593  

V stall = 29.47609 ft/s D (AC) = 0.794593132 lbs

  20.09733 mph TR (cruise) = 0.723374609 lbs

V lo = 35.37131 ft/s PR (cruise) = 26.52614691 ft*lbs/sec

  24.1168 mph   0.048229358 HP

PE = 12000 ft*lbs   36.17201851 Watt

PR (to) = 40.09369 ft*lbs/sec Slo = 132.0693402 ft

  0.072898 HP R/C = 2.484385668 ft/s

  54.67321 Watt      

0

0.5

1

1.5

2

2.5

3

5 10 15 20 25 30 35 40 45 50

Velocity (ft/s)

R/C

(ft

/s)

AXI 4120/18 Motor• Power: 511 Watts

• Max. Efficiency: 86%

• RPM/Volt: 510 RPM/V

• Weight: 0.7 lb

• Propeller: 14”

Thunder Power “Dynamic Power” LiPo Electric Flight Pack

Rating: 5C Max Avg. DischargeOutput:18.5V Nominal, 8200mAhDimension: 50mm x 305mm x 28mm (772gr)

Questions????